Device and method for a spacecraft

ABSTRACT

The invention presented here relates to a device in a spacecraft comprising a carrier rocket, a satellite and a detachable adapter ( 4 ) for connecting a satellite to the carrier rocket, where the adapter ( 4 ) comprises a wall structure ( 14, 15 ) for supporting the satellite on the carrier rocket, and is fixed at its lower rim to the carrier rocket and is fixed at its upper rim to the satellite. The device is characterised in that the adapter ( 4 ) is divided essentially across the longitudinal direction of the spacecraft and that both of the adapter parts ( 12, 13 ) are detachably connected to each other. The invention comprises the said adapter design and a method for separating the invented device.

TECHNICAL FIELD

[0001] The present invention relates to a device in a spacecraftcomprising a first craft part, a second craft part with its payload, anda detachable adapter for connecting the second craft part to the firstcraft part.

[0002] The invention also involves the design of the said adapter, aswell as a method for separating the craft parts in the invented device.

STATE OF THE ART

[0003] A carrier rocket is used for launching craft such as satellitesinto space. The carrier rocket consists of several engines, which one ata time propel the rocket so as to carry it to an orbital point where thesatellite is separated from the carrier rocket. During launching, whenone rocket carrier engine is expended the next one takes over, whereupona part of the carrier rocket comprising the expended engine detachesfrom the rest of the carrier rocket.

[0004] By means of a bolt connection, a carrier rocket adapter ismounted above the engine which powers the rocket carrier the final partof its path towards the orbital point where the satellite is to bedetached. The carrier rocket adapter acts as an interface between thecarrier rocket and cylindrical structural parts of the satellite,whereby a clamp comprising shoes and a band provide a detachableconnection between a carrier rocket adapter and a satellite. In theassembled state the shoes bear on cylindrical structural parts of thesatellite and the carrier rocket's adapter, at the same time as the bandis pre-stressed around the shoes so that these exert compressive forceson the structural parts and the adapter. During satellite separation anopening mechanism in the clamp is activated, whereby the clamp opens andthe satellite is released from the carrier rocket adapter with the aidof separating springs. The carrier rocket adapter has the shape of anenvelope surface of a straight cylinder, or the envelope surface of astraight truncated, straight, circular cone, one rim of which, asdescribed above, is mounted above the upper engine by means of, forexample, a bolt connection, while the other ribbed rim is prevented bythe clamp fitting from moving relative to the ribbed circular structuralparts of the satellite.

[0005] An arrangement involving a smaller satellite between the carrierrocket adapter and the main satellite is also known. This smallersatellite may extend down into the adapter's internal space. The smallersatellite is detachable from the main satellite and can be separatedfrom it after carrier rocket separation.

DESCRIPTION OF INVENTION

[0006] One embodiment of the present invention provides a device for aspacecraft, comprising a first craft part, a second craft part with itspayload, and a detachable adapter for connecting the second craft partto the first craft part, where the adapter contains a wall structurewhich supports the second craft part on the first craft part and isfixed at its lower rim to the first craft part and has at its upper rima detachable connection with the second craft part. The device ischaracterised in that the adapter is divided across the longitudinaldirection of the spacecraft and that the adapter parts are detachablyconnected to each other. In one preferred embodiment the the adapter isdivided into two adapter parts. In another embodiment the adapter isdivided across the longitudinal direction of the spacecraft in severalplaces and thus consists of several adapter parts detachably connectedto each other.

[0007] Moreover, the invention relates to the said adapter as well as amethod for separating the craft parts within the device, which involvesthe second craft part detaching from the spacecraft after which theadapter part fitted to the second craft part is detached from theremaining spacecraft.

[0008] The first craft part is preferably a carrier rocket and thesecond craft part is preferably a satellite.

[0009] In one embodiment the above-mentioned adapter part(s) notconnecting to the carrier rocket has (have) internally dedicatedpositions for equipment for space operation of the adapter part, such assolar panels, power systems, control systems, and on-board computers,but even payloads such as hardware and software for execution of one ormore tasks. Thereby the adapter part can operate as a separateindependent satellite. In an alternative embodiment, the spaces areoccupied by equipment for space operation in the form of smallindependent satellites designed to release from the above-mentionedadapter part after separation. In a further embodiment, the twoabove-mentioned embodiments are combined.

[0010] The device and the method represented by the invention haveseveral advantages compared with previously known technology. Theinvention device allows at least one extra satellite to be launched witheach rocket firing without needing to modify either the structure of thecarrier rocket intended for fitting to the adapter or equivalentstructure on the satellite. The influence of the additional satellite onthe main satellite during the launching phase and the separation phaseis negligible. Furthermore, a greater payload volume can be sent up withevery rocket firing, without impacting on the original payload volume.The usefulness of the device is also greater with regard to weight, asthe adapter is included in the spacecraft irrespective of whether or notit is used as a satellite structure after satellite separation.

DESCRIPTION OF DRAWINGS

[0011]FIG. 1 illustrates schematically an example of a spacecraft.

[0012]FIG. 2 is a perspective drawing of an adapter in the spacecraft inFIG. 1.

[0013]FIG. 3 is a perspective drawing of a part of the adapter in FIG.2.

[0014]FIG. 4 shows a cross-sectional view of a clamp fitting on thespacecraft.

[0015]FIG. 5A shows the adapter part in FIG. 3 from above and FIG. 5Bshows the corresponding adapter part in an alternative embodiment, alsoviewed from above.

PREFERRED EMBODIMENTS

[0016] In FIG. 1 the number 1 denotes a spacecraft comprising a carrierrocket 2 and a detachable craft part 3, in the form of a satellite inthe example here. The carrier rocket 2 is constructed of several engines(not shown), which one at a time power the space craft 1 so as to carryit to an orbital point where the satellite 3 is separated from thecarrier rocket 2. During launching, when one rocket carrier engine isexpended, the next one takes over, whereupon a part of the carrierrocket comprising the expended engine detaches from the rest of thecarrier rocket. An adapter 4 is mounted above the carrier rocket 2engine, which propels the spacecraft 1 the final part of its coursetowards the orbital point where the satellite 3 is to be detached. Thesatellite 3 is mounted above the adapter 4; the adapter 4 acts as aninterface between the carrier rocket 2 and the satellite 3. The adapter4 comprises an upper adapter part 12, which, as will be described belowin more detail, is detachably fitted to cylindrical structural parts 11of the satellite 3, and a lower adapter part 13 fitted, for example bybolting, riveting, gluing, or a combination of these, above the lastengine section of the carrier rocket.

[0017] Each carrier rocket part 12, 13 in FIG. 2 comprises a wall

[0018]14, 15 in the shape of an envelope surface of a straighttruncated, straight, circular cone, where the radius of the wall of theupper adapter part's 12 lower rim 16 essentially coincides with the wallradius of the lower adapter part's 13 upper rim 17. In the exampleshown, the angle of incline of the upper adapter wall 14 is greater thanthe angle of incline of the lower adapter wall 15. In an alternativeembodiment, the angles of incline of both adapter walls 14, 15 areequally big, while in a further embodiment the angle of incline of theupper adapter wall 14 is less than the angle of incline of the loweradapter wall 15. In the example shown, the lower adapter wall 15 islonger than the upper; in an alternative embodiment, the adapter wallsare the same lengths and in a further embodiment, the upper adapter wallis longer than the lower. As well as the adapter 4 being divided, it isconstructed according to conventional measurements in order to fit tothe carrier rocket and standard interfaces with satellites, and with thesame performance as regards strength, etc as existing conventionaladapters.

[0019] In FIG. 4, the upper adapter part's 12 wall 14 at its lower rim16 is furnished with a flange 6 constructed either integrated with thewall 14 as one part, or as a separate part, which is fixed, by rivetingfor example, to the lower rim 16 of the wall 14. Similarly, the loweradapter part's 13 wall 15 at its upper rim 17 is furnished around theoutside with a flange 7. A clamp 8 comprising flanged 6,7 shoes 10positioned at regular intervals and a band 9 surrounding the shoes jointhe parts 12, 13 of the adapter 4. An opening mechanism (not shown) inthe clamp, on being activated, is arranged to open the clamp, so thatthe adapter parts 12, 13 have a detachable connection with each other.

[0020] The upper rim 10 shown in FIG. 2 also has a flange around theoutside and the cylindrical structural parts 11 of the satellite 3 aresupplied with flanges. A clamp such as the one described in connectionwith FIG. 4 forms a detachable connection between the satellite and theadapter part 12, with the shoes resting against the satellite'scylindrical structural parts 11 and the adapter part 12, at the sametime as a band is pre-stressed around the shoes so that these exertcompressive forces on the satellite and the adapter, thus preventingthem from moving in relation to one another.

[0021] In FIGS. 3 and 5A, the adapter part 12 has internally dedicatedattachment positions 18 for various equipment. The amount and complexityof equipment may vary, and may, for example, include all the equipmentneeded for an independent satellite, such as solar panels, propulsionsystems, control systems and on-board computers. Those attachmentpositions 18 not required for satellite operation may be used forpayload, for example hardware and software for executing one or moretasks. FIG. 5B shows an alternative configuration of positions 18 in theadapter part; the only limitation being that the positions 18 must notencroach on the space reserved for parts such as protruding parts of thesatellite and/or the carrier rocket. In an alternative embodiment, eachof several mounting positions 18 is occupied by a small, independentsatellite, so that after clamp separation the adapter part 12 is used asa “dispenser” for releasing small satellites. The adapter part 12preferably has a control system and a propulsion system for driving theadapter part 12 to a position that is specific for each small satelliteand where the satellite is released. Apart from acting as an interfacebetween the carrier rocket's upper engine module and the satellite 3, aswell as being a load carrying structure for the satellite 3, a part 12of the adapter 4 together with the equipment contained thereinconstitutes an independent spacecraft after clamp separation.

[0022] The above-described spacecraft is designed to operate as follows.When the last carrier rocket engine is expended and the satellite 3 hasadopted its desired course, an opening mechanism in the clamp betweenthe satellite and the upper adapter part is activated, whereby the clampopens and the satellite 3 is released from the adapter 4, thus renderingit free to adopt its course in space. Thereafter, the clamp joining theadapter parts opens, whereupon the adapter part 12 is able to leave thecarrier rocket and adopt a course in space aided by the equipment in thededicated positions.

1. A device in a spacecraft (1), comprising a first craft part (2), asecond craft part (3) with its payload, and a detachable adapter (4) forconnecting the second craft part (3) to the first craft part (2), wherethe adapter (4) comprises a wall structure (14, 15) which supports thesecond craft part (3) on the first craft part, and is fixed at its lowerrim to the first craft part and is fixed at its upper rim to the secondcraft part, characterised in that the adapter (4) is divided in at leastone place across the longitudinal direction of the spacecraft and thatthe adapter parts (12, 13) are detachably connected to each other.
 2. Adevice as in claim 1, characterised in that one adapter part (12) of theadapter (4) is detachably connected to the second craft part (3)
 3. Adevice as in claim 1, characterised in that the adapter part (12) hasinternally dedicated positions (18) for equipment for space operation.4. A device as in claim 1, characterised in that the wall structure (14,15) is constructed as a truncated cone.
 5. A method for separating thecraft parts within the device as in claim 1, characterised in that thesecond craft part (3) detaches from the spacecraft (1) after which theadapter part (12) is detached from the remaining spacecraft.
 6. Anadapter for a spacecraft (1) designed to detachably join a first craftpart (2) with a second craft part (3) with its payload, where theadapter (4) comprises a wall structure (14, 15) for supporting thesecond craft part (3) on the first craft part (2), and where the wallstructure (14, 15) at its lower rim is designed to be fixed to the firstcraft part and at its upper rim to be fixed to the second craft part,characterised in that adapter (4) is divided essentially across thelongitudinal direction of the spacecraft and that both of the adapterparts (12, 13) are detachably connected to each other.
 7. A device in aspacecraft (1), comprising a carrier rocket (2), a satellite (3) and adetachable adapter (4) for connecting the satellite (3) to the carrierrocket (2), where the adapter (4) comprises a wall structure (14, 15)for supporting the satellite (3) on the carrier rocket (2), and is fixedat its lower rim to the carrier rocket and is fixed at its upper rim tothe satellite, characterised in that the adapter (4) is dividedessentially across the longitudinal direction of the spacecraft and thatboth of the adapter parts (12, 13) are detachably connected to eachother.
 8. A device as in claim 1, characterised in that one adapter part(12) of the adapter (4) is detachably connected to the satellite (3). 9.A device as in claim 1, characterised in that the adapter part (12) hasinternally dedicated positions (18) for equipment for space operation.10. A device as in claim 1, characterised in that the wall structure(14, 15) is constructed as a truncated cone.
 11. A method for separatingthe craft parts within the device as in claim 7, characterised in thatthe satellite (3) detaches from the spacecraft (1) after which theadapter part (12) is detached from the remaining spacecraft.
 12. Anadapter for a spacecraft (1) designed to detachably join a carrierrocket (2) with a satellite (3), where the adapter (4) comprises a wallstructure (14, 15) for supporting the satellite (3) on the carrierrocket (2), and where the wall structure (14, 15) at its lower rim isdesigned to be fixed to the carrier rocket and at its upper rim to befixed to the satellite, characterised in that the adapter (4) is dividedessentially across the longitudinal direction of the spacecraft and thatboth of the adapter parts (12, 13) are detachably connected to eachother.
 13. A device in a spacecraft, comprising a first craft part, asecond craft part with its payload, and an adapter for detachablyconnecting the second craft part to the first craft part, said adaptercomprising a wall structure which supports the second craft part on thefirst craft part, said wall structure being fixed at its lower rim tothe first craft part and being fixed at its upper rim to the secondcraft part, and said adapter being divided across the longitudinaldirection of the spacecraft in at least one place into adapter partsdetachably connected to each other.
 14. A device in a spacecraft,comprising a carrier rocket, a satellite and an adapter for detechablyconnecting the satellite to the carrier rocket, said adapter comprisinga wall structure for supporting the satellite on the carrier rocket,said wall structure being fixed at its lower rim to the carrier rocketand being fixed at its upper rim to the satellite and said adapter beingdivided essentially across the longitudinal direction of the spacecraftinto a first and a second adapter part detachably connected to eachother.
 15. A device as in claim 14, wherein the first adapter part ofthe adapter is detachably connected to the satellite.
 16. A device as inclaim 15, wherein the first adapter part has internally dedicatedpositions for equipment for space operation.
 17. An adapter for aspacecraft designed to detachably join a first craft part with a secondcraft part comprising payload, where the adapter comprises a wallstructure for supporting the second craft part on the first craft part,and where the wall structure at its lower rim is designed to be fixed tothe first craft part and at its upper rim to be fixed to the secondcraft part, the adapter being divided essentially across thelongitudinal direction of the spacecraft into adapter parts detachablyconnected to each other.
 18. An adapter for a spacecraft designed todetachably join a carrier rocket with a satellite, where the adaptercomprises a wall structure for supporting the satellite on the carrierrocket, and where the wall structure at its lower rim is designed to befixed to the carrier rocket and at its upper rim to be fixed to thesatellite, the adapter being divided essentially across the longitudinaldirection of the spacecraft into adapter parts detachably connected toeach other.
 19. A method for separating a first craft part from a secondcraft part of a space craft, wherein an adapter detachably connects thesecond craft part to the first craft part, said adapter being dividedacross the longitudinal direction of the spacecraft in at least oneplace into adapter parts detachably connected to each other, the methodcomprising the steps of detaching the second craft part from an upperpart of the adapter and then detaching said upper adapter part from theremaining spacecraft.
 20. A method for separating a carrier rocket froma satellite, wherein an adapter detachably connects the satellite to thecarrier rocket, said adapter being divided across the longitudinaldirection into an upper adapter part facing the satellite and a loweradapter part facing the carrier rocket, said adapter parts beingdetachably connected to each other, the method comprising the steps ofdetaching the satellite from the upper part of the adapter and thendetaching said upper adapter part from the lower adapter part.